JPH0219098A - Command transmitter-receiver - Google Patents
Command transmitter-receiverInfo
- Publication number
- JPH0219098A JPH0219098A JP63169703A JP16970388A JPH0219098A JP H0219098 A JPH0219098 A JP H0219098A JP 63169703 A JP63169703 A JP 63169703A JP 16970388 A JP16970388 A JP 16970388A JP H0219098 A JPH0219098 A JP H0219098A
- Authority
- JP
- Japan
- Prior art keywords
- frequency
- receiver
- launching
- transmitter
- signal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000010355 oscillation Effects 0.000 claims description 3
- 230000006866 deterioration Effects 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 3
- 238000010304 firing Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 101150101918 TSC22D3 gene Proteins 0.000 description 1
- 241000270708 Testudinidae Species 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Selective Calling Equipment (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
この発明は、航空機に搭載され、その航空機から発射さ
れる飛しよう体に対し方向指示をするためのコマンド信
号を送る。送受信システムにおける送受信機に関するも
のである。DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention is mounted on an aircraft and sends a command signal to give direction to a flying object launched from the aircraft. The present invention relates to a transmitter/receiver in a transmitter/receiver system.
第2図は従来のコマンド送受信機を示す図であシ1図に
おいて、(1)は航空機に搭載される送信機。FIG. 2 is a diagram showing a conventional command transmitter/receiver. In FIG. 1, (1) is a transmitter mounted on an aircraft.
(2)は飛しよう体に搭載される受信機である。(2) is a receiver mounted on the flying object.
送信機(1)において、(3)は送信コマンドデータ。In the transmitter (1), (3) is transmission command data.
(4)は送信コマンドデータ(3)を変調する変調器、
(至)は変調器(4)K搬送波(6)を供給するための
発振器。(4) is a modulator that modulates the transmission command data (3);
(to) a modulator (4) and an oscillator for supplying the K carrier wave (6).
(7)は変調器(4)から出力された変調波、(8)は
変調波(7)を増幅する増幅器、(9)は送信アンテナ
、 01は搬送波である。(7) is a modulated wave output from the modulator (4), (8) is an amplifier that amplifies the modulated wave (7), (9) is a transmitting antenna, and 01 is a carrier wave.
受信機(2)において、a優は受信アンテナ、CIIは
増幅器、C211は増幅器(至)で増幅された受信信号
、四は周波数変換器、(至)は周波数変換器(2)に局
部信号@を供給する発振器、@は増幅器、ceは増幅さ
れた中間周波信号、鋤は中間周波信号(至)を復調する
復調器、csは復調器で復調された受信コマンドデータ
である。In the receiver (2), a is the receiving antenna, CII is the amplifier, C211 is the received signal amplified by the amplifier (to), 4 is the frequency converter, and (to) is the local signal @ to the frequency converter (2). @ is an amplifier, ce is an amplified intermediate frequency signal, plow is a demodulator that demodulates the intermediate frequency signal (to), and cs is received command data demodulated by the demodulator.
次に動作について説明する。Next, the operation will be explained.
航空機に搭載された送信機+11において、送信コマン
ドデータ(3)は変調器(4)にょシ変調され、変調波
(7)となる。変調の際、搬送波(6)は発振器(2)
から供給される。変調波(7)は増幅器(8)により増
幅され。In the transmitter +11 mounted on the aircraft, the transmitted command data (3) is modulated by a modulator (4) to become a modulated wave (7). During modulation, the carrier wave (6) is the oscillator (2)
Supplied from. The modulated wave (7) is amplified by an amplifier (8).
送信アンテナ(9)から搬送波+IQとして送信される
。It is transmitted from the transmitting antenna (9) as a carrier wave + IQ.
飛しよう体に搭載された受信機(2)において、受信ア
ンテナα[有]で受信した搬送波α・は増幅器(至)で
増幅され受信信号e2Dとなる。この受信信号c2Dは
発振器(至)から供給される局部信号(財)によシ1周
波数変換器(2)で周波数変換され、増幅器(至)を経
て中間周波信号(至)として復調器■に入力される。そ
して復調器■によシ受信コマンドデータ(至)が取シ出
される。In the receiver (2) mounted on the flying object, the carrier wave α received by the receiving antenna α is amplified by the amplifier (to) and becomes a received signal e2D. This received signal c2D is frequency-converted by a frequency converter (2) using a local signal supplied from an oscillator (to), and then sent to a demodulator as an intermediate frequency signal (to) via an amplifier (to). is input. The received command data (to) is then extracted by the demodulator (2).
従来のコマンド送受信機は以上のように、送信側と受信
側で局部発振器をそれぞれ別々に内蔵している。As described above, the conventional command transmitter/receiver has separate local oscillators built in on the transmitting side and the receiving side.
一般に発振器は、環境条件等によシ周波数ずれが生じる
ので、送受それぞれの発振周波数は初期設定値からずれ
を生じる。このずれは復調器勾に入力される中間周波信
号(1)の周波数すれとなる。In general, frequency deviations occur in oscillators due to environmental conditions, etc., so the oscillation frequencies for transmitting and receiving each deviate from the initial setting values. This deviation becomes a frequency deviation of the intermediate frequency signal (1) input to the demodulator gradient.
復調器勾において、復調するには復調できる帯域幅にそ
のずれに対応できるだけの広さが必要である。その帯域
幅がコマンドデータのデータレートに比べ非常に広い場
合は、復調信号のs1m比の劣化を招き、受信性能の劣
化となる。In the demodulator gradient, in order to perform demodulation, the demodulating bandwidth must be wide enough to accommodate the deviation. If the bandwidth is much wider than the data rate of command data, the s1m ratio of the demodulated signal deteriorates, resulting in deterioration of reception performance.
例として、送信波0呻の搬送周波数をI Q、14 G
Hz。As an example, the carrier frequency of the transmitted wave 0 is IQ, 14G
Hz.
受信機の局部信号@を10GIlz、 コマンドデータ
(3)及び(2)のデータレートを10KHzとする。Assume that the local signal @ of the receiver is 10 GIlz, and the data rate of command data (3) and (2) is 10 KHz.
発振器(至)及び(2)の温度安定度を±50 ppm
とする。航空機においては、温度条件は一40℃〜+8
0℃と非常に厳しい。まず送信側の発振器が±50pp
mずれたとすると、搬送波α〔はIQ、14GHzx(
±50 ppm )−±501 KHzのずれとなる。Temperature stability of oscillator (to) and (2) to ±50 ppm
shall be. In aircraft, the temperature conditions are -40°C to +8°C.
The temperature is extremely severe at 0℃. First, the oscillator on the transmitting side is ±50pp.
If the carrier wave α [is IQ, 14 GHz x (
±50 ppm) - ±501 KHz.
受信側ではこのずれに加え、受信側発振器のずれ100
)lzx(±50ppm)−±500 KHzがあシ、
送信側と合わせて±I MHzを超すずれとなる。ここ
で、送信側のコマンドデータのデータレートが10KH
zで、送受信機に内蔵の発振器の周波数ずれがなければ
、10KHzの帯域で復調可能となるが、実際には発振
器のずれによシ・±1007KHzの帯域が必要となる
。これは。On the receiving side, in addition to this deviation, the receiving side oscillator deviation is 100
)lzx(±50ppm)-±500 KHz,
Together with the transmitting side, the deviation exceeds ±I MHz. Here, the data rate of the command data on the sending side is 10KH.
If there is no frequency deviation in the oscillator built into the transmitter/receiver, demodulation is possible in a band of 10 KHz, but in reality, a band of ±1007 KHz is required due to the deviation in the oscillator. this is.
8/N比で約23dBの劣化となる。The deterioration is approximately 23 dB at an 8/N ratio.
この発明はこのような課題を解決するためになされたも
ので、受信機ハードウェア規模を変えることなく、狭帯
域化しs/N劣化を防ぎ受信性能を向上させることがで
きるコマンド送受信機を得ることを目的とする。This invention was made to solve these problems, and it is an object of the present invention to obtain a command transmitter/receiver that can narrow the band, prevent S/N deterioration, and improve reception performance without changing the receiver hardware scale. With the goal.
この発明に係るコマンド送受信機は、送信機内の位相同
期回路を受信機内の発振器に同期させ。The command transceiver according to the present invention synchronizes the phase synchronization circuit in the transmitter with the oscillator in the receiver.
飛しよう体発射後も発射前と同じ周波数に保つことので
きるものである。Even after a projectile is launched, it can maintain the same frequency as before the launch.
この発明におけるコマンド送受信機は、送信機内に位相
同期回路を、受信機内に発振器を内蔵することによシ、
受信機のハードウェア規模を変えることなく狭帯域化し
、8/N比の劣化を防ぐことができる。The command transmitter/receiver according to the present invention incorporates a phase synchronization circuit in the transmitter and an oscillator in the receiver.
It is possible to narrow the band without changing the hardware scale of the receiver and prevent deterioration of the 8/N ratio.
以下、この発明の一実施例を図について説明する。 An embodiment of the present invention will be described below with reference to the drawings.
第1図において、αυは位相同期回路、(5)はてい倍
器、aりは電圧制御発振器、(11は電圧制御発振器(
I2の出力と受信側の局部信号(財)を入力とする位相
比較器、α尋はループフィルタ、 Q9はループフィル
タα尋の出力をホールド信号αeによりテンプルホール
ドするサンプルホールド回路、 aSは飛しよう体発射
前に送信機と受信機を接続しているコネクタ。In Figure 1, αυ is a phase-locked circuit, (5) is a multiplier, a is a voltage-controlled oscillator, (11 is a voltage-controlled oscillator (
A phase comparator that receives the output of I2 and the local signal on the receiving side as input, α-hiro is a loop filter, Q9 is a sample-hold circuit that holds the output of loop filter α-hiro using a hold signal αe, and aS should be skipped. A connector that connects the transmitter and receiver before launch.
顛は飛しよう体発射時にホールド信号を出力するホール
ド信号発生器である。The main part is a hold signal generator that outputs a hold signal when launching a flying object.
次に動作について説明する。Next, the operation will be explained.
飛しよう体発射前において0位相比較器(13には。0 phase comparator (13) before launching the projectile.
受信側から局部信号@がコネクタ舖を経て入力されてお
シ1位相同期回路αυは位相同期ループですでに同じ周
波数に保たれている。このとき、サンプルホールド回路
clcJはループフィルタα尋出力を′亀圧制御発撮器
a′aへそのまま送信している。A local signal @ is input from the receiving side via the connector, and the first phase locked circuit αυ is already kept at the same frequency in the phase locked loop. At this time, the sample hold circuit clcJ transmits the output of the loop filter α as it is to the tortoise pressure control generator a'a.
飛しよう体発射後、コネクタasは接続がはずれ。After launching the flying object, the connector AS becomes disconnected.
位相比較器α3への一方の入力が断となるので位相同期
ループは開放となる。しかし9発射と同時にホールド信
号aQがサンプルホールド回路α9へ送られ9発射直前
に電圧制御発振器aりに加えられていた制御電圧が保持
される。したがって、電圧制御発振器αりの出力は1発
射前ど同じ周波数が保たれている。よって、てい倍器(
5)の出力、すなわち受信用の局部信号(6)は発射後
も送信側の局部信号(財)と同じ周波数に保たれている
。Since one input to the phase comparator α3 is disconnected, the phase locked loop becomes open. However, at the same time as the 9th firing, a hold signal aQ is sent to the sample and hold circuit α9, and the control voltage that was applied to the voltage controlled oscillator a immediately before the 9th firing is held. Therefore, the output of the voltage controlled oscillator α remains at the same frequency as before one firing. Therefore, the multiplier (
The output of 5), that is, the local signal for reception (6), is maintained at the same frequency as the local signal on the transmitting side even after being emitted.
復調器(5)においては、入力されてくる中間周波信号
(至)が送信側の搬送周波数と発射後もずれを生じない
ため狭帯域にすることが可能で、その結果。In the demodulator (5), since the input intermediate frequency signal (to) does not deviate from the carrier frequency on the transmitting side even after being emitted, it is possible to narrow the band.
復調信号の8A比の劣化を防ぐことができる。Deterioration of the 8A ratio of the demodulated signal can be prevented.
なお、上記実施例では送信機側にサンプルホールド回路
aSにホールド信号aeを与える際ホールド信号発生器
σηを用いたものを示したが9代わシに航空機から飛し
よう体発射信号を受は飛しよう体飛しよう中発射前の周
波数を保持する構成としてもよい。In the above embodiment, the hold signal generator ση is used to give the hold signal ae to the sample-and-hold circuit aS on the transmitter side. It may also be configured to maintain the frequency before the launch while the body is about to fly.
以上のように、この発明によれば、飛しよう体発射前に
受信機内の発振器に送信機内の局部発振器の周波数を一
致させた位相同期回路を送信機内に搭載する構成とした
ので、飛しよう体に搭載する受信機は従来構成L:りま
ま受信機の狭帯域化が図れ、 B7’H比の劣化を防ぐ
効果がある。As described above, according to the present invention, the transmitter is equipped with a phase synchronization circuit that matches the frequency of the local oscillator in the transmitter with the oscillator in the receiver before launching the flying object. The receiver installed in the B7'H has the conventional configuration L: The receiver has a narrower band and is effective in preventing deterioration of the B7'H ratio.
第1図はこの発明の一実施例によるコマンド送受信機を
示す図、第2図は従来のコマンド送受信機を示す図であ
る。
(1)は送信機、(2)は受信機、Qυは位相同期回路
。
α1はサンプルホールド回路、舖はコネクタ。
なお1図中、同一符号は同一、又は相当部分を示す。FIG. 1 is a diagram showing a command transmitter/receiver according to an embodiment of the present invention, and FIG. 2 is a diagram showing a conventional command transmitter/receiver. (1) is a transmitter, (2) is a receiver, and Qυ is a phase locked circuit. α1 is the sample hold circuit or connector. In addition, in FIG. 1, the same reference numerals indicate the same or equivalent parts.
Claims (1)
送受信システムにおいて、航空機に送信機を、航空機か
ら発射される飛しよう体に受信機をそれぞれ搭載し、飛
しよう体発射前に受信側から送信側へ搬送波を供給する
コネクタと、送信側に受信側からのその搬送周波数と同
じ周波数の送信用局部発振周波数を得る位相同期回路と
、その送信用局部発振周波数を飛しよう体発射後も発射
前と同じ周波数を保つためのサンプルホールド回路とを
備えたコマンド送受信機。In a transmission/reception system that transmits command signals from an aircraft to a flying object, a transmitter is mounted on the aircraft and a receiver is mounted on the flying object launched from the aircraft. A connector that supplies a carrier wave to the transmitting side, a phase synchronization circuit that obtains a transmitting local oscillation frequency of the same frequency as the carrier frequency from the receiving side on the transmitting side, and a phase synchronization circuit that provides a transmitting local oscillation frequency that is the same as the carrier frequency from the receiving side. Command transceiver with sample and hold circuit to keep the same frequency.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP63169703A JPH0219098A (en) | 1988-07-07 | 1988-07-07 | Command transmitter-receiver |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP63169703A JPH0219098A (en) | 1988-07-07 | 1988-07-07 | Command transmitter-receiver |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH0219098A true JPH0219098A (en) | 1990-01-23 |
Family
ID=15891315
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP63169703A Pending JPH0219098A (en) | 1988-07-07 | 1988-07-07 | Command transmitter-receiver |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH0219098A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS62205037A (en) * | 1986-03-03 | 1987-09-09 | Asahi Chem Ind Co Ltd | Production of cycloolefin |
US5457251A (en) * | 1992-01-24 | 1995-10-10 | Asahi Kasei Kogyo Kabushiki Kaisha | Method for partially hydrogenating a monocyclic aromatic hydrocarbon |
-
1988
- 1988-07-07 JP JP63169703A patent/JPH0219098A/en active Pending
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS62205037A (en) * | 1986-03-03 | 1987-09-09 | Asahi Chem Ind Co Ltd | Production of cycloolefin |
JPH0335299B2 (en) * | 1986-03-03 | 1991-05-27 | Asahi Chemical Ind | |
US5457251A (en) * | 1992-01-24 | 1995-10-10 | Asahi Kasei Kogyo Kabushiki Kaisha | Method for partially hydrogenating a monocyclic aromatic hydrocarbon |
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